DELFT DU84-132V3 AIRFOIL (MEASURED) (du84132v-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: DELFT DU84-132V3 AIRFOIL (MEASURED) (du84132v-il) Reynolds number: 50,000 Max Cl/Cd: 34.3 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-du84132v-il-50000-n5.txt Download as CSV file: xf-du84132v-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: DELFT DU84-132V3 AIRFOIL (MEASURED)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4202 0.09521 0.08780 -0.0544 1.0000 0.0655
-9.750 -0.4251 0.09176 0.08442 -0.0544 1.0000 0.0651
-9.500 -0.4340 0.08787 0.08061 -0.0548 1.0000 0.0645
-9.250 -0.4492 0.08340 0.07622 -0.0556 1.0000 0.0638
-9.000 -0.4728 0.07917 0.07207 -0.0558 1.0000 0.0632
-8.750 -0.5032 0.07580 0.06877 -0.0545 1.0000 0.0626
-8.500 -0.5336 0.07250 0.06549 -0.0529 1.0000 0.0621
-8.250 -0.5580 0.06890 0.06183 -0.0516 1.0000 0.0615
-8.000 -0.5772 0.06522 0.05802 -0.0503 1.0000 0.0610
-7.750 -0.5909 0.06146 0.05406 -0.0492 1.0000 0.0606
-7.500 -0.5976 0.05789 0.05022 -0.0482 1.0000 0.0601
-7.250 -0.5987 0.05447 0.04649 -0.0474 1.0000 0.0598
-7.000 -0.5947 0.05127 0.04294 -0.0467 1.0000 0.0596
-6.750 -0.5840 0.04827 0.03955 -0.0466 0.9992 0.0596
-6.500 -0.5545 0.04505 0.03584 -0.0496 0.9932 0.0598
-6.250 -0.5247 0.04239 0.03273 -0.0519 0.9870 0.0602
-6.000 -0.4922 0.04013 0.03005 -0.0541 0.9814 0.0609
-5.750 -0.4623 0.03825 0.02783 -0.0554 0.9751 0.0617
-5.500 -0.4291 0.03664 0.02589 -0.0571 0.9693 0.0632
-5.250 -0.3974 0.03532 0.02423 -0.0582 0.9629 0.0655
-5.000 -0.3662 0.03417 0.02309 -0.0594 0.9563 0.0685
-4.750 -0.3331 0.03319 0.02200 -0.0606 0.9502 0.0721
-4.500 -0.3040 0.03232 0.02095 -0.0608 0.9426 0.0752
-4.250 -0.2698 0.03140 0.02000 -0.0621 0.9372 0.0796
-4.000 -0.2451 0.03063 0.01915 -0.0618 0.9288 0.0857
-3.750 -0.2127 0.02974 0.01829 -0.0632 0.9230 0.0984
-3.500 -0.1871 0.02888 0.01762 -0.0635 0.9153 0.1197
-3.250 -0.1577 0.02757 0.01697 -0.0651 0.9088 0.2003
-3.000 -0.1309 0.02618 0.01663 -0.0662 0.9028 0.3862
-2.750 -0.1121 0.02580 0.01684 -0.0642 0.8946 0.5053
-2.500 -0.0960 0.02639 0.01803 -0.0589 0.8886 0.6262
-2.250 -0.0814 0.02703 0.01857 -0.0557 0.8786 0.7011
-2.000 -0.0539 0.02759 0.01891 -0.0543 0.8728 0.7522
-1.750 -0.0415 0.02793 0.01912 -0.0508 0.8626 0.7849
-1.500 -0.0168 0.02798 0.01901 -0.0490 0.8569 0.8164
-1.250 -0.0057 0.02798 0.01892 -0.0453 0.8469 0.8415
-1.000 0.0221 0.02778 0.01856 -0.0444 0.8414 0.8638
-0.750 0.0377 0.02773 0.01841 -0.0419 0.8314 0.8842
-0.500 0.0729 0.02752 0.01807 -0.0424 0.8260 0.9072
-0.250 0.1055 0.02754 0.01798 -0.0432 0.8168 0.9290
0.000 0.1590 0.02741 0.01769 -0.0478 0.8114 0.9437
0.250 0.1980 0.02743 0.01759 -0.0504 0.8019 0.9543
0.750 0.2971 0.02727 0.01720 -0.0590 0.7865 0.9735
1.000 0.3571 0.02707 0.01691 -0.0650 0.7810 0.9839
1.250 0.3995 0.02708 0.01687 -0.0682 0.7711 0.9986
1.500 0.4300 0.02684 0.01656 -0.0687 0.7624 1.0000
1.750 0.4596 0.02649 0.01616 -0.0688 0.7529 1.0000
2.000 0.4728 0.02645 0.01609 -0.0664 0.7404 1.0000
2.250 0.4859 0.02643 0.01604 -0.0640 0.7277 1.0000
2.500 0.5056 0.02637 0.01594 -0.0626 0.7164 1.0000
2.750 0.5329 0.02623 0.01577 -0.0624 0.7066 1.0000
3.000 0.5649 0.02601 0.01554 -0.0628 0.6974 1.0000
3.250 0.5817 0.02624 0.01577 -0.0613 0.6846 1.0000
3.500 0.6043 0.02639 0.01593 -0.0606 0.6731 1.0000
3.750 0.6316 0.02647 0.01603 -0.0606 0.6626 1.0000
4.000 0.6694 0.02624 0.01579 -0.0619 0.6539 1.0000
4.250 0.6916 0.02648 0.01607 -0.0611 0.6407 1.0000
4.500 0.7169 0.02664 0.01628 -0.0608 0.6277 1.0000
4.750 0.7443 0.02678 0.01645 -0.0607 0.6149 1.0000
5.000 0.7704 0.02699 0.01671 -0.0605 0.6017 1.0000
5.250 0.7972 0.02722 0.01699 -0.0604 0.5883 1.0000
5.500 0.8278 0.02731 0.01712 -0.0607 0.5755 1.0000
5.750 0.8623 0.02726 0.01708 -0.0615 0.5626 1.0000
6.000 0.8885 0.02752 0.01739 -0.0612 0.5473 1.0000
6.250 0.9120 0.02790 0.01781 -0.0606 0.5314 1.0000
6.500 0.9363 0.02825 0.01820 -0.0601 0.5157 1.0000
6.750 0.9605 0.02861 0.01862 -0.0596 0.5000 1.0000
7.000 0.9822 0.02907 0.01913 -0.0587 0.4839 1.0000
7.250 1.0002 0.02963 0.01974 -0.0574 0.4671 1.0000
7.500 1.0183 0.03006 0.02021 -0.0560 0.4500 1.0000
7.750 1.0396 0.03031 0.02044 -0.0549 0.4335 1.0000
8.000 1.0542 0.03090 0.02105 -0.0531 0.4165 1.0000
8.250 1.0710 0.03150 0.02167 -0.0517 0.4009 1.0000
8.500 1.0925 0.03200 0.02215 -0.0508 0.3864 1.0000
8.750 1.1081 0.03280 0.02300 -0.0494 0.3710 1.0000
9.000 1.1209 0.03373 0.02400 -0.0477 0.3556 1.0000
9.250 1.1325 0.03473 0.02510 -0.0460 0.3405 1.0000
9.500 1.1431 0.03577 0.02623 -0.0442 0.3254 1.0000
9.750 1.1536 0.03685 0.02736 -0.0425 0.3104 1.0000
10.000 1.1634 0.03801 0.02861 -0.0408 0.2955 1.0000
10.250 1.1703 0.03937 0.03003 -0.0390 0.2799 1.0000
10.500 1.1758 0.04082 0.03154 -0.0372 0.2640 1.0000
10.750 1.1804 0.04241 0.03315 -0.0355 0.2483 1.0000
11.000 1.1820 0.04429 0.03509 -0.0339 0.2320 1.0000
11.250 1.1823 0.04635 0.03723 -0.0324 0.2162 1.0000
11.500 1.1830 0.04848 0.03940 -0.0312 0.2021 1.0000
11.750 1.1848 0.05065 0.04157 -0.0302 0.1900 1.0000
12.000 1.1884 0.05278 0.04365 -0.0293 0.1800 1.0000
12.250 1.1906 0.05534 0.04635 -0.0287 0.1696 1.0000
12.500 1.1940 0.05776 0.04880 -0.0281 0.1613 1.0000
12.750 1.1986 0.06015 0.05122 -0.0277 0.1539 1.0000
13.000 1.2035 0.06266 0.05380 -0.0272 0.1470 1.0000
13.250 1.2101 0.06497 0.05610 -0.0268 0.1401 1.0000
13.500 1.2124 0.06797 0.05925 -0.0266 0.1335 1.0000
13.750 1.2145 0.07090 0.06226 -0.0266 0.1267 1.0000
14.000 1.2118 0.07457 0.06611 -0.0269 0.1209 1.0000
14.250 1.2060 0.07862 0.07035 -0.0276 0.1154 1.0000
14.500 1.2044 0.08207 0.07385 -0.0282 0.1100 1.0000
14.750 1.1931 0.08723 0.07927 -0.0298 0.1056 1.0000
15.000 1.1931 0.09057 0.08264 -0.0306 0.1009 1.0000
15.250 1.1897 0.09480 0.08699 -0.0318 0.0972 1.0000
15.500 1.1733 0.10152 0.09403 -0.0346 0.0945 1.0000
15.750 1.1575 0.10835 0.10108 -0.0378 0.0920 1.0000
16.000 1.1488 0.11400 0.10687 -0.0403 0.0893 1.0000
16.250 1.1647 0.11487 0.10763 -0.0397 0.0855 1.0000
16.500 1.1284 0.12654 0.11963 -0.0465 0.0848 1.0000
16.750 1.0682 0.14549 0.13879 -0.0583 0.0848 1.0000
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Polar data table (+)
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